CN107769845A - Star double light path alignment ground validation system - Google Patents
Star double light path alignment ground validation system Download PDFInfo
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- CN107769845A CN107769845A CN201710942898.8A CN201710942898A CN107769845A CN 107769845 A CN107769845 A CN 107769845A CN 201710942898 A CN201710942898 A CN 201710942898A CN 107769845 A CN107769845 A CN 107769845A
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B10/00—Transmission systems employing electromagnetic waves other than radio-waves, e.g. infrared, visible or ultraviolet light, or employing corpuscular radiation, e.g. quantum communication
- H04B10/07—Arrangements for monitoring or testing transmission systems; Arrangements for fault measurement of transmission systems
- H04B10/075—Arrangements for monitoring or testing transmission systems; Arrangements for fault measurement of transmission systems using an in-service signal
- H04B10/077—Arrangements for monitoring or testing transmission systems; Arrangements for fault measurement of transmission systems using an in-service signal using a supervisory or additional signal
- H04B10/0775—Performance monitoring and measurement of transmission parameters
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B10/00—Transmission systems employing electromagnetic waves other than radio-waves, e.g. infrared, visible or ultraviolet light, or employing corpuscular radiation, e.g. quantum communication
- H04B10/11—Arrangements specific to free-space transmission, i.e. transmission through air or vacuum
- H04B10/118—Arrangements specific to free-space transmission, i.e. transmission through air or vacuum specially adapted for satellite communication
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B10/00—Transmission systems employing electromagnetic waves other than radio-waves, e.g. infrared, visible or ultraviolet light, or employing corpuscular radiation, e.g. quantum communication
- H04B10/70—Photonic quantum communication
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L9/00—Cryptographic mechanisms or cryptographic arrangements for secret or secure communications; Network security protocols
- H04L9/08—Key distribution or management, e.g. generation, sharing or updating, of cryptographic keys or passwords
- H04L9/0816—Key establishment, i.e. cryptographic processes or cryptographic protocols whereby a shared secret becomes available to two or more parties, for subsequent use
- H04L9/0852—Quantum cryptography
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Abstract
Double light path is directed at ground validation system to the present invention with providing a kind of star, including：Star is tested, simulates entity satellite；Air floating table module, supplied comprising the carrying air floating table for testing star and for the air floating table so that the air floating table drives the feeder for testing star fixed-axis rotation；Earth station's analog module, simulator is moved comprising receiving station, communicated for simulating grounded receiving station with the experiment star；Celestial body test module, test data is sent to the experiment star to test the function and performance of the experiment star；Control module is examined on ground, is connected respectively with earth station's analog module and the celestial body test module, controls earth station's analog module to run according to the test data of the celestial body test module., can be with the in-orbit Key Performance Indicator of indirect verification quantum sciences test satellite by the present invention before satellite heaven.
Description
Technical field
The present invention relates to space technology technical field, more particularly to satellite equipment technical field, specially a kind of star
Double light path is directed at ground validation system.
Copyright notice
This patent document disclosure includes material protected by copyright.The copyright owns for copyright holder.Copyright
Owner does not oppose that anyone replicates the patent document in the presence of the proce's-verbal of Patent＆Trademark Office and archives or should
Patent discloses.
Background technology
At present, the capture of general aircraft and earth station or generally use radio or visible ray means are directed at, be often referred to
It is not high to precision, about 0.3~0.5 degree or so.Under this precision, the method for classics need to be only taken to can be achieved.As the world
First quantum sciences test satellite, alignment precision reaches 3.5u radians with requiring star for it, before developing this kind of high-precision satellite, I
With needing star to test satellite double light path alignment scheme carry out ground validation and analysis, to ensure having for the in-orbit experiment of satellite
Effect property.
The content of the invention
In view of the above the shortcomings that prior art, the purpose of embodiments of the invention is a kind of with providing star double light path
Ground validation system is directed at, for carrying out ground validation and analysis to test satellite.
In order to achieve the above objects and other related objects, double light path is directed at ground to embodiments of the invention with providing a kind of star
Checking system, the star double light path alignment ground validation system include：Star is tested, simulates entity satellite；Air floating table module, bag
Supplied containing an air floating table for carrying the experiment star and for the air floating table and cause the air floating table drive experiment star dead axle
The feeder of rotation；Earth station's analog module, comprising receiving station's simulator, for simulating grounded receiving station and the experiment star
Communication；Celestial body test module, test data is sent to the experiment star to test the function and performance of the experiment star；Ground prosecution
Molding block, it is connected respectively with earth station's analog module and the celestial body test module, according to the celestial body test module
Test data controls earth station's analog module operation.
In one embodiment of the invention, the experiment star includes support frame, and the light path being installed on support frame as described above is led to
Module is believed, for controlling the experiment sensing of star, the light path communication module to the beacon beam of receiving station's simulator
Capture, aim at and the attitude control module of tracking, provides the power supply module of power supply for the experiment star and control the light path to communicate
Module, the attitude control module and the power supply module run and gather the quantum key communication equipment and the quantum entanglement hair
The industrial computer for the data that the machine of penetrating receives.
In one embodiment of the invention, the light path communication module includes：Quantum key communication equipment, with being connect described in one
Receive station simulator and establish Quantum Optical Communication channel, comprising cipher key communication ray machine body and control the cipher key communication ray machine body fortune
The first capable electric cabinet；Quantum entanglement emitter, Quantum Optical Communication channel is established with receiving station's simulator, comprising entangling
Twine the second electric cabinet that this running body of transmitting ray machine is tangled described in transmitting ray machine body and control.
In one embodiment of the invention, the light path communication module also includes：Optical fiber laser, respectively with the quantum
Cipher key communication machine carries out laser communication and is simultaneously connected with the industry control module, and control instruction and will be from institute is received from the industry control module
Data transfer that quantum key communication equipment receives is stated to the industry control module.
In one embodiment of the invention, the attitude control module includes optical fibre gyro and counteraction flyback.
In one embodiment of the invention, receiving station's simulator includes the quiet simulator of receiving station and receiving station's dynamic model is intended
Device.
In one embodiment of the invention, the quiet simulator of receiving station includes：Parallel light tube, CCD camera and laser；
The parallel light tube, receive the quantum light that the experiment star is sent and the quantum light of reception is focused on into the CCD camera
On；The laser that the laser is sent enters the parallel light tube after the CCD camera, by the parallel light tube by beacon beam
It is transmitted into the experiment star.
In one embodiment of the invention, the quiet simulator of receiving station also includes：Host computer processing module, it is and described
CCD camera is connected, and from the CCD camera reception amount sub-light image, and measures quantum light according to the quantum light image and aims at light
The shake of axle and the deviation of quantum light and beacon optical axis.
In one embodiment of the invention, the CCD camera is provided with the color separation film being divided to the beacon beam.
In one embodiment of the invention, laser beam analyzer is placed on the reflected light path of the light splitting piece, on transmitted light path
Beacon beam is placed, and multiple corner reflectors are placed in the diverse location of parallel light tube outgoing optical port, and is caused multiple described
Image patch of the reflected light of reflector on the laser beam analyzer is completely superposed.
In one embodiment of the invention, simulator moves in the receiving station includes autocollimator, optical fiber and by institute
State the optic fibre fixing device that optical fiber is fixed on the telescope focal plane.
In one embodiment of the invention, the autocollimator outgoing bore is not less than 300mm, outgoing beacon diverging
Angle is less than 10urad.
In one embodiment of the invention, earth station's analog module includes two receiving stations and moves simulator.
In one embodiment of the invention, the star double light path alignment ground validation system also include driving the reception
Stand the motion guide rail device of simulator.
In one embodiment of the invention, the motion guide rail device includes：Guide rail, carry the receiving station and move simulator
Automatically controlled displacement platform, the motor that move in guide rail of the driving automatically controlled displacement platform and the control for controlling the motor
Device.
In one embodiment of the invention, the length of the guide rail is 5~10m.
In one embodiment of the invention, examining control module describedly includes：Receiving unit, receive the celestial body test mould
The experiment star control data and air floating table module control data of block output；Control unit, according to the receiving unit from the star
The data that body test module receives control earth station's analog module operation.
In one embodiment of the invention, described control unit includes：Computing unit, for calculating the experiment star and institute
State receiving station and move simulator relative position and sensing；Curved unit, the motion guide rail of simulator is moved for generating the receiving station
The sensing controlling curve of simulator moves in position controlling curve and the receiving station；Subelement is controlled, for controlling the receiving station
Dynamic simulator is moved on guide rail and the sensing campaign of the dynamic simulator of the receiving station.
In one embodiment of the invention, described control unit also includes：Data receipt unit, for receiving the reception
Stand simulator, the status data and test data of the quiet simulator of the motion guide rail device and the receiving station；Data record
Unit, the status number of simulator, the quiet simulator of the motion guide rail device and the receiving station is moved for recording the receiving station
According to and test data；Data display unit, for showing that the receiving station moves simulator, the motion guide rail device and described connect
Receive the status data and test data for quiet simulator of standing.
As described above, the present invention star double light path alignment ground validation system have the advantages that：
By the present invention before satellite heaven, it can be referred to the in-orbit key performance of indirect verification quantum sciences test satellite
Mark.
Brief description of the drawings
Technical scheme in order to illustrate the embodiments of the present invention more clearly, make required in being described below to embodiment
Accompanying drawing is briefly described, it should be apparent that, drawings in the following description are only some embodiments of the present invention, for
For those of ordinary skill in the art, on the premise of not paying creative work, other can also be obtained according to these accompanying drawings
Accompanying drawing.
Double light path is directed at the overall theory structure of ground validation system in one embodiment to Fig. 1 with being shown as the star of the present invention
Schematic diagram.
Fig. 2 be shown as the present invention star double light path alignment ground validation system in the quiet simulator of receiving station schematic diagram.
Receiving station quiet simulator focuses light path to Fig. 3 in double light path alignment ground validation system with being shown as the star of the present invention
Schematic diagram.
Double light path is directed at the schematic diagram that simulator moves in receiving station in ground validation system to Fig. 4 with being shown as the star of the present invention.
Fig. 5 be shown as the present invention star double light path alignment ground validation system practical application schematic diagram.
Component label instructions
100 experiment stars
101 light path communication modules
101a quantum key communication equipments
101b quantum entanglement emitters
101c optical fiber lasers
102 attitude control modules
102a optical fibre gyros
102b counteraction flybacks
103 power supply modules
104 inverters
105 industrial computers
110 air floating table modules
121st, simulator moves in 122 receiving stations
121a autocollimators
121b single-mode fibers
The quiet simulator of 123 receiving stations
123a optical fiber lasers
123b CCD cameras
123c parallel light tubes
123d host computers
123e light splitting pieces
123g reflectors
123f laser beam analyzers
130 celestial body test modules
Examine control module in 140 ground
Embodiment
Embodiments of the present invention are illustrated by particular specific embodiment below, those skilled in the art can be by this explanation
Content disclosed by book understands other advantages and effect of the present invention easily.
It should be clear that structure, ratio, size depicted in this specification institute accompanying drawings etc., only coordinating specification to be taken off
The content shown, so that those skilled in the art understands and reads, the enforceable qualifications of the present invention are not limited to, therefore
Do not have technical essential meaning, the modification of any structure, the change of proportionate relationship or the adjustment of size, do not influenceing the present invention
It the effect of can be generated and can reach now, all should still fall and obtain the scope that can cover in disclosed technology contents
It is interior.Meanwhile cited such as " on ", " under " in this specification, "left", "right", the term of " centre " and " one ", also only just
In understanding for narration, and it is not used to limit the enforceable scope of the present invention, its relativeness is altered or modified, without substantive change
Under more technology contents, when being also considered as the enforceable category of the present invention.
The purpose of embodiments of the invention is a kind of with providing star double light path alignment ground validation system, for experiment
Satellite carries out ground validation and analysis.Star of the invention described in detail below double light path alignment ground validation system principle
And embodiment, those skilled in the art is not needed creative work with being appreciated that star of the invention double light path alignment ground
Checking system.
A kind of embodiments of the invention star is provided double light path alignment ground validation system, as shown in figure 1, the star it is double
Light path alignment ground validation system includes：Test star 100, air floating table module 110, earth station's analog module, celestial body test module
130 and ground inspection control module 140.
Below to the experiment star 100 in the present embodiment, air floating table module 110, earth station's analog module, celestial body test module
130 and ground inspection control module 140 be described in detail respectively.
Test star 100, air floating table module 110, earth station's analog module, celestial body test module 130 and ground prosecution molding
The basic composition and parameter of block 140 are as shown in table 1.
Special project is directed at the star of table 1 tests unit table of participating in the experiment
In the present embodiment, the experiment star 100 is used to simulate entity satellite.The experiment star 100 is arranged on air floating table
In module 110, can freely it be rotated with dead axle, the experiment star 100 double light path alignment ground validation as the present embodiment culminant star
The measurand of system test.Star 100 is tested by the gyro and flywheel of attitude control module 102, the battery of power supply module 103, is carried
Quantum key communication equipment 101a, quantum entanglement emitter the 101b composition of lotus.
According to quantum satellite pitching corner and two kinds of situations of corner are rolled, design two kinds of experiment structures of star 100.
Wherein, a kind of experiment star 100 of structure is used for carrying out the test of alignment precision during pitch axes, another knot
The experiment star 100 of structure is used for carrying out the test of alignment precision during axis of rolling rotation.
Specifically, in the present embodiment, the experiment star 100 includes support frame, the light path being installed on support frame as described above
Communication module 101, for controlling the sensing for testing star 100, the light path communication module 101 to receiving station's simulator
Beacon beam capture, aiming and tracking attitude control module 102, for it is described experiment star 100 provide power supply power supply module 103 with
And control light path communication module 101, the attitude control module 102 and the power supply module 103 run and gather the amount
The industrial computer 105 for the data that sub-key communication equipment 101a and the quantum entanglement emitter 101b are received.
Specifically, in the present embodiment, the light path communication module 101 includes：Quantum key communication equipment 101a and quantum
Tangle emitter 101b.
Quantum key communication equipment 101a and receiving station's simulator establish Quantum Optical Communication channel, lead to comprising key
Believe ray machine body and control first electric cabinet of this running body of the cipher key communication ray machine.
Quantum entanglement emitter 101b, Quantum Optical Communication channel is established with receiving station's simulator, comprising tangling
Second electric cabinet of this running body of transmitting ray machine is tangled described in transmitting ray machine body and control.
In the present embodiment, the light path communication module 101 also includes：Optical fiber laser 101c, respectively with the quantum
Cipher key communication machine 101a carries out laser communication and is simultaneously connected with the industry control module, receives control instruction from the industry control module and incites somebody to action
From the data transfer that the quantum key communication equipment 101a is received to the industry control module.
In the present embodiment, the attitude control module 102 includes optical fibre gyro 102a and counteraction flyback 102b.
Test star 100 and the main distinction in the configuration of first sample star is as follows：
1st, the structure of star 100 is tested
Light path is aligned for star, the change and influence as follows that the experiment structure of star 100 is brought：
1) load benchmark optical axis relative position：Test the relativeness of the holding of star 100 and first sample star in load benchmark optical axis
On be consistent, do not influence equivalence.
2) rotary inertia：It is inconsistent to test the rotary inertia of star 100 and first sample star rotary inertia, but rotary inertia and attitude control,
The relation of loading movement coupling is clear and definite, and the experiment rotary inertia of star 100 can be surveyed, and convert and simulate in-orbit state inertia by inertia,
Do not influence equivalence.
3) transmission of micro-vibration：The experiment structure change of star 100 causes the transmission characteristic of micro-vibration to change, therefore tests star
100 micro-vibration characteristics and first sample state inequivalence.
It is using the main reason for organization plan of star 100 is without using the electrical star structure with first sample state consistency is tested：
A) electrically star architecture quality is big, and inertia is excessive after being connected with air floating table rotating part, and the reaction of first sample state flies
102b driving moments deficiency is taken turns, changing flywheel then more influences the validity of special experiment；
B) electrically star architecture quality is big, meets that the air floating table equipment of bearing condition is difficult to select；
C) tested for air floating table, micro-vibration transmission characteristic and in-orbit state inequivalence, do not have after celestial body is connected with air floating table
It is necessary to adopt complete electrically star structure.
2nd, payload configures
Light path is aligned for star, and payload is configured with quantum key communication equipment 101a, quantum entanglement emitter 101b,
It is electrical property product, function meets first sample state of the art requirement with performance, and do not configure quantum entangled source can light path pair to star
Quasi- index measures, and does not influence equivalence.
3rd, platform stand-alone configuration
Light path is aligned for star, satellite platform stand-alone configuration lithium battery, optical fibre gyro 102a and counteraction flyback
102b, with first sample state consistency, other units with star light path be aligned it is unrelated.
It is right during the wherein configuration optical fibre gyro 102a of attitude control module 102 and counteraction flyback 102b, with in-orbit experiment
Stand point to use to determine appearance consistent with control model, do not influence equivalence.
In the present embodiment, the air floating table module 110 includes the air floating table of the carrying experiment star 100 and is described
Air floating table supplies the feeder for causing the air floating table to drive the experiment fixed-axis rotation of star 100.
The air floating table is single-axle air bearing table.
In the present embodiment, the air floating table module 110 also includes the angular instrument being installed on the air floating table, for surveying
Measure the rotational angle of the air floating table.
Wherein, the feeder includes a gas cylinder.
The air floating table module 110 i.e. in the present embodiment is made up of air floating table, gas cylinder and angular instrument, and air floating table is used
Star 100 is tested in support, experiment star 100 is supplied with less friction fixed-axis rotation, gas cylinder for air floating table, angular instrument
Measurement shows the Angle Position of air floating table.
Single-axle air bearing table will rotate stage body by stable and uniform air-flow and suspend, and be provided for carrier single pass under below-G conditions
The condition of attitude dynamics specificity analysis.Air floating table carries angle-measuring equipment, can obtain angular speed to angular difference.In the present embodiment
Single-axle air bearing table main performance index it is as follows：
1) bearing capacity：Not less than 300kg；
2) workbench diameter：1.2m；
3) angle measurement accuracy (absolute precision)：Better than 5 rads (1 σ)；
4) moment of friction：<7gcm；
5) the equivalent tracking error of air floating table micro-vibration：0.6urad (1 σ ,@5Hz~200Hz).
6) supply gas pressure：<0.5Mpa.
In the present embodiment, earth station's analog module includes receiving station's simulator, for simulate grounded receiving station with
The experiment star 100 communicates.
In the present embodiment, receiving station's simulator includes the quiet simulator 123 of receiving station and simulator moves in receiving station
121。
In the present embodiment, the quiet main body of simulator 123 of receiving station uses 17m heavy caliber parallel light tube 123c, fixed
Place, possess transmitting beacon light ability and quantum light-receiving ability after modified instruction, measurable quantum transmitting optical axis points to essence
Degree, it is that the main high-precision quantum transmitting optical axis of experiment points to test equipment.
In the present embodiment, it is dynamic with simulation that the dynamic simulator 121 of the receiving station is placed on motion guide rail relatively whole luck
The track motion of satellite, possess transmitting beacon beam and point to control and emissivities, payload can be traced earth station and move simulator
Beacon beam, output tracking accuracy (miss distance) data.
Specifically, in the present embodiment, as shown in Fig. 2 the quiet simulator 123 of the receiving station includes：Parallel light tube 123c,
CCD camera 123b and laser；The parallel light tube 123c, receive the quantum light that sends of experiment star 100 and by reception
The quantum light is focused on the CCD camera 123b；The laser that the laser is sent enters after the CCD camera 123b
The parallel light tube 123c, beacon beam is transmitted into the experiment star 100 by the parallel light tube 123c.
So in the present embodiment, the quiet simulator 123 of receiving station is by parallel light tube 123c, single mode fiber laser 123a
And CCD camera 123b is formed, and can produce simulated optical earth station far field beacon beam, effect load-tracking is provided with, receives and effectively carries
The quantum light of lotus transmitting, measurement quantum light aim at the shake of optical axis, and the deviation of quantum light and beacon optical axis.
Specifically, the quiet simulator 123 of the receiving station uses 17m focal lengths, bore 1.2m parallel light tube 123c, can meet
Effective covering to payload to be measured.
Single mode fiber laser 123a wavelength is 671nm.Fiber end face is placed at parallel light tube 123c focal plane, according to light
Principle is learned, the beacon light beam in simulation far field can be produced by parallel light tube 123c.Single-mode fiber 121b diameter 5.6um, put down through 17m
After row light pipe 123c, consider that diffraction influences, the light beam of the 2urad angles of divergence can be generated less than in theory.
In originally applying in example, the quiet simulator 123 of receiving station also includes：Host computer processing module, positioned at a host computer
In 123d, it is connected with the CCD camera 123b, from the CCD camera 123b reception amounts sub-light image, and according to the quantum light
Image measurement quantum light aims at shake and the deviation of quantum light and beacon optical axis of optical axis.
In the present embodiment, the CCD camera 123b is provided with the color separation film being divided to the beacon beam.
In the present embodiment, laser beam analyzer 123f is placed on the reflected light path of the light splitting piece 123e, on transmitted light path
Beacon beam is placed, and multiple corner reflector 123g are placed in the diverse location of parallel light tube 123c outgoing optical ports, and is caused
Image patch of the multiple reflector 123g reflected light on the laser beam analyzer 123f is completely superposed.
The CCD camera 123b is similarly positioned at parallel light tube 123c focal planes, is divided with beacon beam transmitting using color separation film
(diaphragm type color separation film can be used, reduce the influence to light path), beacon beam transmitting and quantum light-receiving can be realized simultaneously.It is described
CCD camera 123b is using business CCD camera 123b, bin size 7.4um, frame frequency 200Hz when large area array uses.
The quantum light of load transmitting is focused on CCD camera 123b by parallel light tube 123c to be imaged, according to optical principle
Analysis, imaging facula is quantum light far field Fraunhofer diffraction contracting ratio, and the centroid position of hot spot can represent quantum light sighted direction.
Quiet simulator is emitted into rower to CCD camera 123b receptions with beacon beam in advance to be determined, and is calibrated CCD camera 123b and is received corresponding letter
The equivalent position of light exit direction is marked, benchmark of the position as measurement pointing error, load pointing error is quantum light hot spot
Position and the equivalent position deviation.
In the present embodiment, incident beam direction is judged using CCD camera 123b detection facula position.Hot spot typically constitutes from
According to CCD many pixels, therefore the position of hot spot can be calculated by centroid algorithm.Centroid algorithm can be by detection point
Resolution brings up to sub-pixel.Influenceed by CCD detection noise and space quantization, detecting location resolution ratio can not reach infinitely small.
If minimum resolution distance detectable CCD is Δ d, then corresponding optical axis direction becomes and turned to：Wherein f is
Parallel light tube 123c focal lengths.
Experimental test has been carried out to CCD detection position resolution.Change the beam direction incided in CCD camera 123b,
Produce CCD imaging facula change in location.For used ccd detector, its facula mass center errors in position measurement peak-to-peak value is not
More than ± 0.5um, standard deviation 0.2189um.If the CCD and 17m focal length parallel light tubes 123c is used cooperatively, to detection
The influence of platform beam direction detection error is less than 0.5um/17m=0.03urad.Meet that 0.2urad angle detection is differentiated
Rate.
Influence of the CCD focal planes defocus to quantum light emergent light axis measurement accuracy is as follows：
During experiment, load emission measure sub-light corresponds to parallel light tube 123c diverse location.If ccd detector face
There is deviation in position and the quasi- positions of focal plane of parallel light tube 123c, then the light beam of identical incident direction, can make during light beam sidesway
Into extra error.
Two light beams of the translation distance as Δ L are set, beam exit direction is consistent.Two such light beam passes through parallel light tube
123c image point positions at quasi- position of focal plane are consistent.
If the quasi- focal planes of parallel light tube 123c are deviateed in CCD detection face, facula position separation can be produced.If parallel light tube
123c focal lengths are f, and it is Δ f that CCD, which deviates quasi- focal plane distance, then angle calculation formula is corresponding to image space deviation：
During actual tests, the sidesway range L about ± 0.25m of amount of incident sub-light, parallel light tube 123c focal lengths f are 17m,
If position of focal plane error delta f is 1mm, caused by quantum light direction of the launch measurement error be：Δ p=0.87urad, using 17m
Parallel light tube 123c has carried out experimental test.
Two sources of parallel light at a distance of 250mm are placed before parallel light tube 123c, and (source of parallel light uses single-mode fiber
121b produces with lens).Measurement CCD be initially positioned at quasi- focal plane, by adjust two light sources sensing now two into
As hot spot almost overlaps.Then CCD is deviateed into the different distance of focal plane, measures the deviation of now two light source image spaces.
In the present embodiment, it is as follows that beacon beam focuses the inaccurate influence to receiving and dispatching coaxial measurement：
If parallel light tube 123c beacon beam deviates preferable focal position, the beacon beam that parallel light tube 123c launches
It is not preferable directional light, now the optical axis at the diverse location of light-emitting window will have different directions, and such angle transmitter is put
To diverse location, the optical axis direction that it is reflected back is also different, and the beacon beam optical axis that complete machine receives will have deviation, Jin Erying
Ring measurement accuracy.
After beacon beam defocus Δ f, its emergent light deviates optical axis amount and described with α, is obtained by geometrical relationshipIt can be seen that
With off-axis amount h increase, optical axis deflection angle linearly increases with it, for the 17m parallel light tubes that bore is 1200mm
123c, the optical axis deviation at its edge is about 2 Δ f μ rad, for the 5m parallel light tube 123c that bore is 400mm, the light at its edge
Axle deviation is about 8 Δ f μ rad, and Δ f units are mm herein.
The defocus of laser beam analyzer 123f and beacon beam is to influence the key factor place of measurement accuracy, but can according to light
Inverse principle, if the defocusing amount of laser beam analyzer 123f and beacon beam is just the same, and defocusing amount is within focal depth range, then from
Burnt influence can also be excluded, i.e., the relative position of laser beam analyzer 123f and beacon beam will be controlled strictly.
Focus scheme：As shown in figure 3, light splitting piece 123e reflected light path places laser beam analyzer 123f, transmitted light path is put
Beacon beam, laser beam analyzer 123f and single-mode fiber 121b positions can accurate adjustments.
Multiple corner reflector 123g are placed in the diverse location (center, edge etc.) of parallel light tube 123c outgoing optical ports, such as
Four, while single-mode fiber 121b and laser beam analyzer 123f (front and rear defocus) are adjusted, four tunnel reflected lights of observation are in beam analysis
Image patch on instrument 123f so that four hot spots are almost completely superposed, now it is believed that beacon beam and laser beam analyzer 123f are without phase
To defocus.
The Focus accuracy of such scheme is determined by corner reflector 123g precision.
When angle measurement error caused by the relative defocus of laser beam analyzer 123f and beacon beam of two-beamIt is small
When corner reflector 123g precision, the above-mentioned precision for focusing scheme is just reached, the minimum defocusing amount that now can determine that is(will two corner reflector 123g be placed in parallel light tube 123c bore edge), wherein δ be corner reflector 123g
Precision, φ is parallel light tube 123c bore, takes δ=3 μ rad, φ=12000mm, it is known that Focus accuracy 0.24mm.
In the present embodiment, it is special optical device that simulator 121 moves in the receiving station, is realized in laboratory to earth station
The simulation of beacon, it can be moved with guide rail and optical axis is pointed into satellite.Satellite is in-orbit when carrying out scientific experimentation task, satellite and ground
For the distance stood between 600km to 2000km, the beacon beam degree of divergence that satellite load receives is less than 1urad, and signal intensity
Distance constantly change with star.
In order to simulate earth station's beacon as far as possible, in the present embodiment, the receiving station moves the major technique of simulator 121 and referred to
It is designated as：
1) it is emitted bore：Not less than 300mm；
2) it is emitted the beacon angle of divergence：Less than 10urad；
3) guide rail range of movement is compensated：± 90 degree；
4) celestial body precision is pointed in dynamic movement process：Better than 0.5 degree.
In the present embodiment, as shown in figure 4, simulator 121 moves in the receiving station includes autocollimator 121a, optical fiber
And the optic fibre fixing device that the optical fiber is fixed on the telescope focal plane.
Wherein, the autocollimator 121a outgoing bore is not less than 300mm, and the outgoing beacon angle of divergence is less than
10urad。
In the present embodiment, earth station's analog module includes Liang Ge receiving stations and moves simulator：Receiving station's dynamic model
Intend device 121 and simulator 122 moves in receiving station.Only illustrate, connect so that simulator 121 moves in the receiving station as an example in the present embodiment
The 26S Proteasome Structure and Function that the 26S Proteasome Structure and Function of the dynamic simulator 122 in receipts station moves simulator 121 with the receiving station is identical.
Simulator 121 moves using business heavy caliber autocollimator 121a, bore 300mm in the receiving station.Design light
Fine fixing device, optical fiber is fixed on telescope focal plane, launches beacon beam.It is electronic by the altitude azimuth form for adapting business telescope
Adjustment frame program, realize angular deflection of the telescope tube by planning, the sensing deviation that compensation motorized rails motion is brought.
Specifically, in the present embodiment, the star double light path alignment ground validation system also include driving the reception
Stand the motion guide rail device of simulator 121.
In the present embodiment, the motion guide rail device includes：Guide rail, carry the electricity that simulator 121 moves in the receiving station
The motor and the controller of the control motor that control displacement platform, the driving automatically controlled displacement platform move in guide rail.
So in the present embodiment, the motion guide rail device is made up of guide rail and guide rail controller, is had on guide rail automatically controlled
Displacement platform (i.e. carrying platform), simulator 121 is moved for installing the receiving station.Carrying platform is intended together with receiving station's dynamic model
Device 121 can move along guide rail according to given position curve under the control of the controller, for simulate earth station and satellite it
Between relative motion.
In the present embodiment, the length of the guide rail is 5~10m.
The motion guide rail device mainly emulate quantum sciences test satellite it is in-orbit carry out scientific experimentation when, satellite orbit fortune
The dynamic Orientation differences process relative to science earth station.
The motion guide rail device is made up of three parts substantially：Automatically controlled displacement platform, motor, controller.Motor
And controller mainly determines driving torque, resolution ratio, acceleration-deceleration, signal transacting, uses function (as scanned, circular interpolation) etc.
Performance parameter.Displacement platform is then the heart of system, the key technical indexes such as displacement accuracy, stroke, load, stability, is applicable ring
Border, appearance and size determine by it.
The key of automatically controlled displacement platform is drive screw, guide rail, body material and crudy.It is flat to the motion of automatically controlled displacement platform
Stability, what carrying size influenceed maximum is guide rail quality.Currently used guide rail pattern mainly has dovetail type, V-type rail pair, line
Property bearing, linear slide rail.Performance comparision is as shown in table 2.
The guide rail pattern analysis of the electronic control translation stage of form 2
According to test requirements document and the arrangement of laboratory's area, to meet 9 ° of angle between dual station and satellite links~
85 ° of scope and certain redundancy is left, the stroke Preliminary design of guide rail is 7 meters.
Existing market there is no standard stroke to reach required by testing, and therefore, we are realized using the bind mode of splicing
The electric translation process of long stroke, this can technically be realized, but need to ensure overall adjustment quality in installation and debugging,
This is the key for ensureing performance.Consider that the electronic control translation stage by driving stepper motor, is realized that adjustment of displacement automates, can installed
The guide rail supporting frame of 100mm~1000mm height, is easy to integral installation to adjust.
Motion of the simulator 121 on guide rail is moved using controller to the receiving station to be controlled, simulation earth station phase
To satellite orbit motion, it is necessary to the interference of the measurement to light path alignment precision for avoiding vibration adjoint in motion from bringing, main skill
Art index is as follows：
1) rail length：7m；
2) central loading：>50kg；
3) control accuracy：0.2mm；
4) maximal rate：0.1m/s；
5) peak acceleration：0.01m/s2.
In the present embodiment, the celestial body test module 130 is described to test to the experiment star 100 transmission test data
Test the function and performance of star 100.
The celestial body test module 130 is used for function and the performance test of satellite, mainly including remote measurement, remote control, injection number
According to etc. function, satellite test parameter and event receive, display and filing record.
The celestial body test module 130 is used for function and the performance test for supporting satellite, examines each module in module level bar
Defined function can be completed under part, equipment, file, process, data and troubleshooting for implementing to be related to for test assignment etc.
Management and control device are provided.Celestial body test module 130 used in experiment is mature modules, be will not be repeated here.
In the present embodiment, control module 140 is examined describedly and is surveyed respectively with earth station's analog module and the celestial body
Die trial block 130 is connected, and controls earth station's analog module to run according to the test data of the celestial body test module 130.
Specifically, posture and the orbit information that control module 140 provides according to the celestial body test module 130 are examined describedly
Calculate the receiving station and move the relative position of simulator 121 and directional information, control the receiving station to move simulator 121 on guide rail
Motion, analog satellite miss the stop process；Receive, show, record the receiving station move simulator 121, the motion guide rail device and
The quiet status data of simulator 123 of the receiving station and test data.
The major function of control module 140 is examined according to experiment demand is：
1) information such as orbit parameter, air floating table angle measurement data and the mode of operation that the comprehensive examining system of satellite provides are received；
2) calculate satellite and move simulator relative position relation and points relationship with earth station；
3) generate motion guide rail position controlling curve and earth station moves simulator and points to controlling curve；
4) control earth station to move simulator to move on guide rail；
5) earth station is controlled to move the sensing campaign of simulator；
6) receive, show, record ground move simulator, the quiet simulator status data of motion guide rail subsystem and earth station and
Test data.
Control module 140 is examined describedly and uses common industrial computer 105 as platform, and establishment special-purpose software supports this special project to try
Test, mark is used with the data-interface of the celestial body test module 130, the motion guide rail device, receiving station's simulator
Accurate commercial interface.
Specifically, in the present embodiment, examining control module 140 describedly includes：Receiving unit and control unit.
The receiving unit receives the control data of experiment star 100 and the air floating table mould that the celestial body test module 130 exports
The control data of block 110.
The data control that described control unit receives according to the receiving unit from the celestial body test module 130 is describedly
The analog module operation of face station.
In the present embodiment, specifically, described control unit includes：Computing unit, for calculate it is described experiment star 100 with
The relative position of simulator 121 and sensing are moved by the receiving station；Curved unit, simulator 121 is moved for generating the receiving station
The sensing controlling curve of simulator 121 moves in motion guide rail position controlling curve and the receiving station；Subelement is controlled, for controlling
The receiving station moves simulator 121 and the sensing campaign that simulator 121 is moved with the receiving station is moved on guide rail.
In the present embodiment, described control unit also includes：Data receipt unit, intend for receiving receiving station's dynamic model
The status data and test data of device 121, the quiet simulator 123 of the motion guide rail device and the receiving station；Data records list
Member, the shape of simulator 121, the quiet simulator 123 of the motion guide rail device and the receiving station is moved for recording the receiving station
State data and test data；Data display unit, for showing that simulator 121, the motion guide rail device move in the receiving station
The status data and test data of simulator 123 quiet with the receiving station.
According to content of the test arrangement, star 100, air floating table module 110, earth station's analog module, celestial body test module are tested
130 and ground inspection control module 140 experiment arrangement schematic diagram it is as shown in Figure 5.Arrange, lead according to the testing equipment shown in Fig. 5
67 ° of arrangements of rail and parallel light tube 123c angles, satellite initially points to be in points to (parallel light tube 123c to the quiet simulator of earth station
Axis direction).
In summary, can be with the in-orbit of indirect verification quantum sciences test satellite by the present invention before satellite heaven
Key Performance Indicator.So the present invention effectively overcomes various shortcoming of the prior art and has high industrial utilization.
The above-described embodiments merely illustrate the principles and effects of the present invention, not for the limitation present invention.It is any ripe
Know the personage of this technology all can carry out modifications and changes under the spirit and scope without prejudice to the present invention to above-described embodiment.Cause
This, those of ordinary skill in the art is complete without departing from disclosed spirit and institute under technological thought such as
Into all equivalent modifications or change, should by the present invention claim be covered.
Claims (19)
- A kind of 1. star ground double light path alignment ground validation system, it is characterised in that star ground double light path alignment ground validation system System includes：Star is tested, simulates entity satellite；Air floating table module, supplied comprising the carrying air floating table for testing star and for the air floating table so that the air floating table band The feeder of the dynamic experiment star fixed-axis rotation；Earth station's analog module, comprising receiving station's simulator, communicated for simulating grounded receiving station with the experiment star；Celestial body test module, test data is sent to the experiment star to test the function and performance of the experiment star；Control module is examined on ground, is connected respectively with earth station's analog module and the celestial body test module, according to the celestial body The test data of test module controls earth station's analog module operation.
- 2. star according to claim 1 double light path alignment ground validation system, it is characterised in that it is described experiment star include Support frame, the light path communication module being installed on support frame as described above, for controlling sensing, the light path communication of the experiment star The attitude control module of capture, aiming and tracking of the module to the beacon beam of receiving station's simulator, for it is described experiment star electricity is provided The power supply module and control light path communication module, the attitude control module and the power supply module in source run and gather institute State the industrial computer for the data that quantum key communication equipment and the quantum entanglement emitter receive.
- 3. star according to claim 2 ground double light path alignment ground validation system, it is characterised in that the light path communicates mould Block includes：Quantum key communication equipment, Quantum Optical Communication channel is established with first receiving station's simulator, includes cipher key communication light Owner's body and the first electric cabinet for controlling the cipher key communication optical machine main body operation；Quantum entanglement emitter, Quantum Optical Communication channel is established with receiving station's simulator another described, comprising tangling transmitting light The second electric cabinet of transmitting optical machine main body operation is tangled described in owner's body and control.
- 4. star according to claim 3 ground double light path alignment ground validation system, it is characterised in that the light path communicates mould Block also includes：Optical fiber laser, laser communication is carried out with the quantum key communication equipment respectively and is connected with the industry control module, Control instruction is received from the industry control module and by from the data transfer that the quantum key communication equipment receives to the industry control Module.
- 5. star according to claim 2 double light path alignment ground validation system, it is characterised in that the attitude control module bag Include optical fibre gyro and counteraction flyback.
- 6. star according to claim 1 ground double light path alignment ground validation system, it is characterised in that receiving station simulation Device includes the quiet simulator of receiving station and simulator moves in receiving station.
- 7. star according to claim 6 double light path alignment ground validation system, it is characterised in that the quiet mould of receiving station Intending device includes：Parallel light tube, CCD camera and laser；The parallel light tube, receive the quantum light that the experiment star is sent and the quantum light of reception is focused on into the CCD On camera；The laser that the laser is sent enters the parallel light tube after the CCD camera, by the parallel light tube by beacon Light is transmitted into the experiment star.
- 8. star according to claim 7 double light path alignment ground validation system, it is characterised in that the quiet mould of receiving station Intending device also includes：Host computer processing module, it is connected with the CCD camera, from the CCD camera reception amount sub-light image, and root Shake and the deviation of quantum light and beacon optical axis of optical axis are aimed at according to quantum light image measurement quantum light.
- 9. star according to claim 7 double light path alignment ground validation system, it is characterised in that in the CCD camera Provided with the color separation film being divided to the beacon beam.
- 10. star according to claim 9 double light path alignment ground validation system, it is characterised in that the light splitting piece Laser beam analyzer is placed on reflected light path, beacon beam is placed on transmitted light path, and in the difference of parallel light tube outgoing optical port Multiple corner reflectors are placed in position, and make it that image patch of the reflected light of multiple reflectors on the laser beam analyzer is complete Overlap.
- 11. star according to claim 6 double light path alignment ground validation system, it is characterised in that the receiving station is moved Simulator includes autocollimator, optical fiber and the optical fiber fixation dress that the optical fiber is fixed on the telescope focal plane Put.
- 12. star according to claim 11 double light path alignment ground validation system, it is characterised in that the reflective prestige Remote mirror outgoing bore is not less than 300mm, and the outgoing beacon angle of divergence is less than 10urad.
- 13. star according to claim 11 double light path alignment ground validation system, it is characterised in that earth station's mould Intend module and include the dynamic simulator of two receiving stations.
- 14. star according to claim 11 or 13 ground double light path alignment ground validation system, it is characterised in that the star Double light path alignment ground validation system also includes the motion guide rail device for driving the receiving station to move simulator.
- 15. star according to claim 14 double light path alignment ground validation system, it is characterised in that the motion guide rail Device includes：Guide rail, carry the receiving station and move the automatically controlled displacement platform of simulator, the driving automatically controlled displacement platform in guide rail movement Motor and the control motor controller.
- 16. star according to claim 15 double light path alignment ground validation system, it is characterised in that the length of the guide rail Spend for 5~10m.
- 17. star according to claim 1 double light path alignment ground validation system, it is characterised in that described ground prosecution system Module includes：Receiving unit, receive the experiment star control data and air floating table module control data of the celestial body test module output；Control unit, the data received according to the receiving unit from the celestial body test module control the earth station to simulate mould Block is run.
- 18. star according to claim 17 double light path alignment ground validation system, it is characterised in that described control unit Including：Computing unit, simulator relative position and sensing are moved with the receiving station for calculating the experiment star；Curved unit, the motion guide rail position controlling curve of simulator and receiving station's dynamic model are moved for generating the receiving station Intend the sensing controlling curve of device；Subelement is controlled, moves the finger of simulator with the receiving station for controlling the dynamic simulator of the receiving station to be moved on guide rail To motion.
- 19. star according to claim 18 double light path alignment ground validation system, it is characterised in that described control unit Also include：Data receipt unit, simulator, the quiet mould of the motion guide rail device and the receiving station are moved for receiving the receiving station Intend the status data and test data of device；Data record unit, simulator, the quiet mould of the motion guide rail device and the receiving station are moved for recording the receiving station Intend the status data and test data of device；Data display unit, for showing that simulator, the quiet mould of the motion guide rail device and the receiving station move in the receiving station Intend the status data and test data of device.
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| CN109188679A (en) * | 2018-10-30 | 2019-01-11 | 宁波光舟通信技术有限公司 | Method of adjustment, device and the lens apparatus of lens apparatus |
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| CN113535619A (en) * | 2021-06-30 | 2021-10-22 | 北京航天时代光电科技有限公司 | High-speed serial interface for satellite based on Virtex-5 series FPGA and TLK2711 |
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